Title (fr)

Publication

Application

Priority

US 21586298 A 19981218

Abstract (en)

A liner (16, 18) for a gas turbine engine combustor (10), includes an upstream section, a downstream section oriented at an angle to the upstream liner section, and a cooling nugget (48, 49) joining the upstream and downstream liner sections for providing mechanical stiffness at a junction of the upstream and downstream liner sections. The cooling nugget (48, 49) further includes a first portion (54) connected to the upstream liner section, a second portion (56) connected to the downstream liner section, and a third portion (58) joining the first and second cooling nugget portions (54, 56) at a first end, the third cooling nugget portion (58) extending radially from the first end, wherein the cooling nugget is in flow communication with a cool air supply and is configured to provide a starter film of cooling air along respective surfaces of the upstream liner section and the downstream liner section. <IMAGE>